Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

EH 1.0/9.0 (eh1090-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: EH 1.0/9.0 (eh1090-il)
Reynolds number: 100,000
Max Cl/Cd: 43.26 at α=6.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-eh1090-il-100000.txt
Download as CSV file: xf-eh1090-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EH 1.0/9.0                                      
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.5865   0.08901   0.08447  -0.0015   1.0000   0.1160
  -8.250  -0.6059   0.08419   0.07974  -0.0077   1.0000   0.1196
  -8.000  -0.6469   0.07949   0.07492  -0.0149   1.0000   0.1221
  -7.750  -0.5730   0.06695   0.06276  -0.0153   1.0000   0.1349
  -7.500  -0.6150   0.07143   0.06698  -0.0122   1.0000   0.1318
  -6.750  -0.6265   0.04716   0.04109  -0.0175   1.0000   0.0694
  -6.500  -0.6148   0.04116   0.03421  -0.0152   1.0000   0.0557
  -6.250  -0.5980   0.03743   0.03016  -0.0139   1.0000   0.0548
  -6.000  -0.5831   0.03368   0.02592  -0.0124   1.0000   0.0563
  -5.750  -0.5640   0.03045   0.02238  -0.0112   1.0000   0.0574
  -5.500  -0.5421   0.02760   0.01909  -0.0097   1.0000   0.0573
  -5.250  -0.5191   0.02518   0.01641  -0.0085   1.0000   0.0591
  -5.000  -0.4949   0.02320   0.01424  -0.0073   1.0000   0.0625
  -4.750  -0.4708   0.02143   0.01225  -0.0061   1.0000   0.0697
  -4.500  -0.4477   0.02009   0.01079  -0.0049   1.0000   0.0816
  -4.250  -0.4269   0.01843   0.00936  -0.0036   1.0000   0.1012
  -4.000  -0.4072   0.01703   0.00811  -0.0018   1.0000   0.1360
  -3.750  -0.3899   0.01567   0.00715   0.0000   1.0000   0.1913
  -3.500  -0.3753   0.01414   0.00636   0.0021   1.0000   0.2912
  -3.250  -0.3691   0.01223   0.00603   0.0062   1.0000   0.5631
  -3.000  -0.3552   0.01186   0.00636   0.0113   1.0000   0.7733
  -2.750  -0.3301   0.01219   0.00670   0.0143   1.0000   0.8652
  -2.500  -0.2763   0.01285   0.00709   0.0119   1.0000   0.9261
  -2.250  -0.1776   0.01337   0.00709   0.0000   1.0000   0.9583
  -2.000  -0.0804   0.01326   0.00658  -0.0131   1.0000   0.9855
  -1.750  -0.0182   0.01280   0.00590  -0.0206   1.0000   1.0000
  -1.500  -0.0041   0.01259   0.00566  -0.0193   1.0000   1.0000
  -1.250   0.0063   0.01246   0.00554  -0.0173   1.0000   1.0000
  -1.000   0.0066   0.01249   0.00560  -0.0138   1.0000   1.0000
  -0.750  -0.0166   0.01281   0.00595  -0.0071   1.0000   1.0000
  -0.500   0.0412   0.01291   0.00598  -0.0140   0.9843   1.0000
  -0.250   0.1084   0.01285   0.00585  -0.0222   0.9667   1.0000
   0.000   0.1700   0.01268   0.00565  -0.0290   0.9444   1.0000
   0.250   0.2201   0.01251   0.00544  -0.0333   0.9165   1.0000
   0.500   0.2539   0.01242   0.00528  -0.0340   0.8857   1.0000
   0.750   0.2759   0.01243   0.00522  -0.0325   0.8538   1.0000
   1.000   0.2958   0.01249   0.00519  -0.0305   0.8250   1.0000
   1.250   0.3147   0.01259   0.00521  -0.0283   0.7986   1.0000
   1.500   0.3337   0.01271   0.00523  -0.0262   0.7742   1.0000
   1.750   0.3533   0.01286   0.00532  -0.0243   0.7495   1.0000
   2.000   0.3735   0.01304   0.00542  -0.0226   0.7262   1.0000
   2.250   0.3942   0.01322   0.00554  -0.0208   0.7051   1.0000
   2.500   0.4153   0.01343   0.00572  -0.0194   0.6823   1.0000
   2.750   0.4367   0.01364   0.00586  -0.0178   0.6619   1.0000
   3.000   0.4583   0.01387   0.00608  -0.0165   0.6400   1.0000
   3.250   0.4802   0.01412   0.00626  -0.0151   0.6201   1.0000
   3.500   0.5023   0.01438   0.00657  -0.0138   0.5985   1.0000
   3.750   0.5246   0.01464   0.00678  -0.0125   0.5789   1.0000
   4.000   0.5469   0.01492   0.00710  -0.0113   0.5571   1.0000
   4.250   0.5694   0.01521   0.00735  -0.0100   0.5370   1.0000
   4.500   0.5917   0.01549   0.00767  -0.0087   0.5142   1.0000
   4.750   0.6140   0.01577   0.00801  -0.0075   0.4918   1.0000
   5.000   0.6364   0.01607   0.00829  -0.0062   0.4695   1.0000
   5.250   0.6588   0.01640   0.00871  -0.0050   0.4461   1.0000
   5.500   0.6810   0.01673   0.00908  -0.0038   0.4218   1.0000
   5.750   0.7025   0.01698   0.00937  -0.0024   0.3932   1.0000
   6.000   0.7229   0.01712   0.00948  -0.0008   0.3585   1.0000
   6.250   0.7419   0.01721   0.00966   0.0007   0.3115   1.0000
   6.500   0.7605   0.01758   0.00997   0.0022   0.2511   1.0000
   6.750   0.7679   0.01996   0.01136   0.0046   0.1111   1.0000
   7.000   0.7782   0.02240   0.01341   0.0069   0.0738   1.0000
   7.250   0.7940   0.02413   0.01511   0.0087   0.0609   1.0000
   7.500   0.8130   0.02581   0.01688   0.0104   0.0548   1.0000
   7.750   0.8327   0.02823   0.01919   0.0117   0.0508   1.0000
   8.000   0.8552   0.03079   0.02196   0.0129   0.0486   1.0000
   8.250   0.8751   0.03280   0.02430   0.0142   0.0450   1.0000
   8.500   0.8939   0.03519   0.02701   0.0153   0.0425   1.0000
   8.750   0.9102   0.03832   0.03051   0.0167   0.0420   1.0000
   9.000   0.9211   0.04192   0.03464   0.0184   0.0423   1.0000
   9.250   0.9252   0.04606   0.03935   0.0203   0.0434   1.0000
   9.500   0.9239   0.05044   0.04421   0.0221   0.0447   1.0000
   9.750   0.9179   0.05485   0.04901   0.0235   0.0459   1.0000
  10.000   0.9078   0.05925   0.05369   0.0247   0.0471   1.0000
  10.250   0.8951   0.06328   0.05791   0.0257   0.0480   1.0000
  10.500   0.8802   0.06750   0.06225   0.0261   0.0488   1.0000
  10.750   0.8779   0.07181   0.06669   0.0260   0.0511   1.0000
  11.000   0.8488   0.07666   0.07172   0.0227   0.0514   1.0000
  11.250   0.8163   0.08400   0.07919   0.0160   0.0517   1.0000
  11.500   0.7106   0.08466   0.08008   0.0150   0.0495   1.0000
  11.750   0.6926   0.09230   0.08781   0.0107   0.0508   1.0000
<< Back to EH 1.0/9.0 (eh1090-il)

Polar data table (+)

Polar graphs


<< Back to EH 1.0/9.0 (eh1090-il)